Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle, and readable storage medium

ABSTRACT

A heat dissipation structure includes a housing configured to accommodate a heating element of an unmanned aerial vehicle (UAV). The housing includes a first air vent and a second air vent. The first air vent is configured to guide an airflow into the housing. The airflow includes a propeller-generated airflow generated by a propeller of the UAV during rotation. A side projection of the first air vent on a side of the housing at least partially overlaps a side projection of the propeller on the side of the housing. The second air vent is configured to guide the airflow out of the housing.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of International Application No.PCT/CN2018/073510, filed Jan. 19, 2018, the entire content of which isincorporated herein by reference.

TECHNICAL FIELD

The present disclosure relates to the field of heat dissipationtechnology and, in particular, to a heat dissipation structure, a heatdissipation method and device, an unmanned aerial vehicle (UAV), and areadable storage medium.

BACKGROUND

A UAV is an unmanned aircraft operated by a radio remote control deviceor a remote control device to perform a mission. In recent years, UAVshave been developed and applied in many fields, such as civilian,industrial and military applications.

In order to improve the user experience and enhance safety, a lot ofelectronic components are used inside the body of the UAV or the powerconsumption of the electronic components is increased. However, moreheat will be generated inside the body. If the heat cannot be dissipatedin time, it will most likely cause the UAV to malfunction.

SUMMARY

In accordance with the disclosure, there is provided a heat dissipationstructure including a housing configured to accommodate a heatingelement of an unmanned aerial vehicle (UAV). The housing includes afirst air vent and a second air vent. The first air vent is configuredto guide an airflow into the housing. The airflow includes apropeller-generated airflow generated by a propeller of the UAV duringrotation. A side projection of the first air vent on a side of thehousing at least partially overlaps a side projection of the propelleron the side of the housing. The second air vent is configured to guidethe airflow out of the housing.

Also in accordance with the disclosure, there is provided an unmannedaerial vehicle (UAV) including a housing, a heating element accommodatedin the housing, an arm connected to the housing, and a propellerconnected to the arm. The housing includes a first air vent and a secondair vent. The first air vent is configured to guide an airflow into thehousing. The airflow includes a propeller-generated airflow generated bythe propeller. A side projection of the first air vent on a side of thehousing at least partially overlaps a side projection of the propelleron the side of the housing. The second air vent is configured to guidethe airflow out of the housing.

BRIEF DESCRIPTION OF THE DRAWINGS

To more clearly illustrate the technical solution of the presentdisclosure, the accompanying drawings used in the description of thedisclosed embodiments are briefly described below. The drawingsdescribed below are merely some embodiments of the present disclosure.Other drawings may be derived from such drawings by a person withordinary skill in the art without creative efforts.

FIG. 1 is a schematic perspective view of an unmanned aerial vehicle(UAV) according to an embodiment of the disclosure.

FIG. 2 is a schematic perspective view of the UAV shown in FIG. 1 fromanother perspective.

FIG. 3 is a schematic exploded perspective view of the UAV shown in FIG.1 .

FIG. 4 is an enlarged view of a part of the cover of the UAV shown inFIG. 3 .

FIG. 5 is a flowchart of a heat dissipation method according to anembodiment of the present disclosure.

FIG. 6 is a schematic block diagram of a heat dissipation deviceaccording to an embodiment of the present disclosure.

DETAILED DESCRIPTION OF THE EMBODIMENTS

The technical solutions in the example embodiments of the presentdisclosure will be described clearly and completely with reference tothe accompanying drawings. The described embodiments are only some ofthe embodiments of the present disclosure, rather than all theembodiments. Based on the embodiments of the present disclosure, allother embodiments obtained by a person of ordinary skill in the artwithout creative efforts shall fall within the scope of the presentdisclosure.

Example embodiments will be described with the reference to theaccompanying drawings, in which the same numbers refer to the same orsimilar elements unless otherwise specified. The implementationsdescribed in the following example embodiments do not represent allimplementations consistent with the present disclosure. Rather, they aremerely examples of devices and methods consistent with some aspects ofthe invention as detailed in the appended claims.

The terminology used in the present disclosure is for the purpose ofdescribing particular embodiments only and is not to limit the presentdisclosure. The singular forms “a,” “said,” and “the” as used in thisdisclosure include the plural forms, unless the context clearlyindicates otherwise. The term “and/or” refers to any or all possiblecombinations of one or more of the associated items. Unless otherwisenoted, “front,” “rear,” “lower” and/or “upper” and similar words are forthe convenience of description only and are not limited to one locationor one spatial orientation. “Connected” or “connecting” and similarwords are not limited to physical or mechanical connections, but mayinclude electrical connections, whether direct or indirect.

A heat dissipation structure, an unmanned aerial vehicle (UAV) and aheat dissipation method of the present disclosure will be described indetail with reference to the accompanying drawings. In the case of noconflict, the features in the following examples and implementations canbe combined with each other and referred to each other.

FIG. 1 is a schematic perspective view of a UAV 100 consistent with thedisclosure. FIG. 2 is another schematic perspective view of the UAV 100from another perspective. The UAV 100 can be used for aerialphotography, mapping, and monitoring, but is not limited thereto. Insome other embodiments, for example, the UAV 100 can also be used foragriculture, express delivery, and providing network services. In someembodiments, the UAV 100 includes a body, an arm 20, a power assembly, acarrier 90 mounted under the body, and a stand. In order to enable thoseskilled in the art to better understand the technical solution andadvantages of embodiments of the disclosure, the overall structure ofthe UAV is first introduced based on FIGS. 1 and 2 from differentperspectives.

As shown in FIG. 1 , the power assembly includes a propeller 30. Thepower assembly may further include a motor (not shown in FIG. 1 ) and anelectronic speed control (ESC, not shown in FIG. 1 ). The propeller 30is driven to rotate by the motor, thereby providing power for ascending,moving forward, rotating, etc. of the UAV 100. The propeller 30 mayinclude a blade and a hub. The hub is fixed to the output shaft of themotor, and the blade is mounted on the hub. When the output shaft of themotor drives the hub to rotate, the blades mounted at the hub alsofollow the rotation to form an area of rotation, and guide the airaround the propeller 30 toward the region below the area of rotation,that is, form a downwash flow to provide lift to the UAV 100. The areaof rotation refers to, e.g., a planar circle area swept by a bladeduring rotating. The ESC can be used to control the operation of themotor and is electrically connected to the flight control circuit boarddescribed below to control the start/stop, rotation speed, steering,etc. of the motor according to the control signals sent by the flightcontrol circuit board, thereby controlling the flight direction andspeed of the UAV 100.

Further, there may be multiple propellers 30, thereby forming amultirotor UAV. In some embodiments, the plurality of propellers 30 maybe arranged around the body, that is, the plurality of propellers 30 maybe arranged at intervals on the outer edge of a housing 40 of the body.In some embodiments, the UAV 100 includes four propellers 30, and thefour propellers 30 may be symmetrically arranged about the horizontalaxis and the longitudinal axis of the UAV 100.

The arm 20 is used to connect the propeller 30 and the body. In someembodiments, the arm 20 may be a single hollow rod made of materialssuch as metal, plastic, or carbon fiber. In some other embodiments, thearm 20 may also be a plate-shaped structure or a solid rod. Thepropeller 30 is fixed to one end of the arm 20 away from the body, andthe other end of the arm 20 is fixed to a housing 40 of the body to bedescribed below. In some embodiments, the propeller 30 is detachably orrotatably installed at the end of the arm 20 away from the body, so asto facilitate storage and transportation of the UAV. Similarly, theother end of the arm 20 can also be detachably or rotatably connected tothe housing 40 of the body, thereby improving the convenience of storageor transportation of the UAV.

In some embodiments, as shown in FIG. 1 , the UAV is a multirotor UAVincluding a plurality of arms 20, and these arms 20 are arranged aroundthe body of the UAV. The number of the power assemblies is the same asthe number of the arms 20, and each propeller 30 is mounted at the endof one of the arms 20 away from, i.e., distal from, the body. Forexample, a mounting hole can be provided at the end of the arm 20 awayfrom the body, and a motor mounting base can be provided at the mountinghole. The motor of the power assembly is fixed at the mounting base, andthe hub of the propeller 30 is fixed at the output shaft of the motor.The ESC can be integrated with the motor, or the ESC can be installed ina chamber of the arm 20.

Further, as shown in FIG. 2 , the UAV is a quadrotor UAV having a frontend, a rear end opposite to the front end, and two sides of the bodyconnecting the front and rear ends. A slot may be provided at the bottomof the front end of the UAV body and recess toward the inside of the UAVbody, and an accommodation space of the slot can be used to accommodatethe carrier 90 while satisfying the design of the UAV body. As a result,the space is fully used, and the carrier 90 can be protected by theaccommodation space. The carrier 90 can be used to support a load. Inthe example shown in FIG. 2 , the carrier 90 may be a gimbal, and theload may be an imaging device such as a camera, a video camera, aninfrared camera, an ultraviolet camera, etc., an audio capture device,or other sensors. Further, the gimbal can be a two-axis gimbal or athree-axis gimbal, so that the gimbal can be adjusted to rotate arounddifferent axes, therefore the UAV 100 has multiple different shootingangles.

In some embodiments, in addition to the above-described mountingpositions, the carrier 90 can also be disposed at the bottom of the rearend of the UAV body, which can be decided according to the UAV model,the body design and usage needs, and is not limited here.

A stand is used to support the UAV on the ground or on a platform on theground when the UAV is landing, so as to prevent the housing 40 fromcontacting the ground or the platform on the ground, therefore thegimbal mounted at the bottom of the housing 40 or the housing 40 can beprotected. The stand can be fixedly connected to the bottom of thehousing 40, or can be disposed under the arm 20, or the bottom of thehousing 40 and the arm 20 can be provided with a stand. The stand can bea buffer structure formed with soft rubber material.

FIG. 3 is an exploded perspective view of the UAV shown in FIG. 1 .Referring to FIG. 3 , the body is the main part of the UAV 100 andincludes a housing 40 and a heating element 50 accommodated in thehousing 40. In some embodiments, the heating element 50 may be anymodel, any type of electronic component, or integrated circuit that isinstalled in the housing 40 for the UAV to realize functions such asflight, shooting, positioning, and navigation. For example, a flightcontrol circuit board, a gyroscope, a wireless receiving circuit, animage transmitting and receiving circuit electrically connected to thecamera on the gimbal, etc. may be installed in the housing 40. In someembodiments, the heating element 50 is a flight control circuit board.

Due to the increasing number of electronic components or integratedcircuits installed or integrated in the housing 40, the heat generatedfrom the current UAV increases a lot compared to the heat generated fromthe UAV produced or developed before. In order for the UAV to workproperly, it is necessary to dissipate the heat generated by the heatingelement 50 to the outside of the housing 40 as soon as possible, so asto reduce the temperature in the housing 40 to within the temperaturerange in which the heating element 50 can work normally.

The present disclosure provides a heat dissipation structure configuredto dissipate heat from the heating element 50 of the UAV, so that thetemperature of the heating element 50 is maintained within a normalworking temperature range. The heat dissipation structure includes ahousing 40 for accommodating the heating element 50 of the UAV 100, andthe housing 40 is provided with a first air vent 41 and a second airvent 42. The first air vent 41 is used to guide the airflow generatedwhen the propeller 30 of the UAV 100 rotates into the housing 40, sothat the heat transfer happens between the airflow and the heatingelement 50, and then the airflow after the heat transfer is led out ofthe housing 40 from the second air vent 42 to achieve the heatdissipation effect on the heating element 50. The side projection of thefirst air vent 41 and the side projection of the propeller 30 at leastpartially overlap. The direction of the side projection here refers tothe side direction of the UAV's body, that is, the projection of thefirst air vent 41 and the projection of the propeller 30 at leastpartially overlap when projecting to the side of the UAV's body.

During the flight of the UAV, the propeller 30 can form an area ofrotation when rotating. On the one hand, when the propeller 30 rotates,the propeller 30 drives the surrounding air to move in the direction inwhich the propeller 30 rotates. Due to air resistance, part of theairflow rotating around the propeller 30 leaves the surface of thepropeller 30 and runs along a tangential direction of the area ofrotation. On the other hand, the air around the propeller 30 can alsoform a downwash flow below the area of rotation. Since the sideprojection of the first air vent 41 and the side projection of thepropeller 30 at least partially overlap, based on this design, theairflow running along the tangential direction of the area of rotation,or the airflow running along the tangential direction of the area ofrotation and the downwash flow can enter the housing 40 through thefirst air vent 41. Further, since the UAV 100 usually flies high in thesky, the temperature of the surrounding air is generally lower. Thelow-temperature airflow entering the housing 40 from the first air vent41 can cool down the heating element 50 well and does not increase thenoise of the UAV 100.

The housing 40 can be made into a circle, an oval, a rectangle, oranother regular or irregular geometric shape. Based on the abovedescription of the body of the UAV, correspondingly, the housing 40 hasa front end and a rear end relative to the front end. The front end ofthe housing may be the nose of the UAV, and the rear end of the housingmay be the tail of the UAV. In the example shown in the figures, thehousing 40 has a rectangular shape with rounded corners. In some otherembodiments, the housing 40 may have any other shape, and the first airvent 41 and the second air vent 42 may be disposed at the housing 40 ofany shape.

As shown in FIG. 3 , the housing 40 includes a casing 47 and a cover 48that is engaged with the casing 47. The casing 47 and the cover 48 forman accommodation chamber to accommodate heating elements 50 and abattery 80 can be mounted at the bottom of the casing 47. The cover 48may be the top of the housing 40, and the first air vent 41 is disposedat the cover 48 and located close to an end of the cover 48. The firstair vent 41 may include two groups corresponding to the pair ofpropellers 30 provided at the rear end of the housing 40, and the twogroups of the first air vents 41 may be symmetrical about thelongitudinal axis of the housing 40, which is not limited here. Inanother embodiment, the two groups of first air vents 41 may beasymmetric about the longitudinal axis of the housing 40. In anotherembodiment, only one set of the first air vent 41 may be provided,corresponding to one of the propellers 30 provided at the rear end ofthe housing 40. In some other embodiments, the first air vents 41 mayalso be disposed at the front end of the cover 48, corresponding to apair of propellers 30 or one of the propellers 30 provided at the frontend of the housing 40.

One group of first air vents 41 may have one or more vent holes, and theshape of a vent hole may be circular, square, oval, or the like. Thenumber, shape, size, etc. of the first air vent 41 are not limited inthe present disclosure, as long as the airflow running along thetangential direction of the area of rotation of the propeller 30, or theairflow running along the tangential direction of the area of rotationof the propeller 30 and the downwash flow may be guided into the housing40.

In some embodiments, since the first air vent 41 needs to guide theairflow, generated when the propeller 30 rotates, into the housing 40,the height of the upper end of the first air vent 41 may be higher thanor equal to the height of the upper end of the propeller 30. Further,the lower end of the first air vent 41 may be not higher than the lowerend of the propeller 30. In this way, more airflow running along thetangential direction of the area of rotation of the propeller 30 and/ordownwash flow can enter the housing 40 from the first air vent 41, andthe cooling and heat dissipation effect is better.

The first air vent 41 may adopt another design different from thestructure design described above. For example, in one embodiment, theheight of the upper end of the first air vent 41 may be lower than theheight of the upper end of the propeller 30 and higher than the heightof the lower end of the propeller 30, and the height of the lower end ofthe first air vent 41 is not higher than the height of the lower end ofthe propeller 30. In some other embodiments, the upper end of the firstair vent 41 is higher than or equal to the upper end of the propeller30, and the lower end of the first air vent 41 is higher than the lowerend of the propeller 30 and lower than the upper end of the propeller30. There is no limitation here.

In the example shown in FIG. 3 , the cover 48 of the housing 40 isprovided with a first plate 43, a second plate 44, and a connection wall45 connecting the first plate 43 and the second plate 44. The first airvent 41 is disposed at the connection wall 45, and the platform heightof the first plate 43 is different from the platform height of thesecond plate 44. In some embodiments, the platform height of the firstplate 43 may be higher than the height of the upper end of the propeller30, and the platform height of the second plate 44 may be lower than theheight of the lower end of the propeller 30. Therefore, when thepropeller 30 rotates to form the area of rotation, the projection of thesecond plate 44 on a plane on which the area of rotation lies may atleast partially overlap the area of rotation. Further, due to the designof the platform height of the first plate 43, the height of the upperend of the first air vent 41 can be higher than or equal to the heightof the upper end of the propeller 30. In this way, the downwash flowformed when the propeller 30 rotates hits the second plate 44 during thedownward flow and changes the flow direction, and the part of thedownwash flow after changing the flow direction enters the housing 40through the first air vent 41. Therefore, on the basis of the airflowrunning along the tangential direction of the area of rotation of thepropeller 30, the airflow into the housing 40 is increased, and thecooling effect is further improved.

In some embodiments, the top of the housing 40 may also have anothershape, such as a curved surface or a spherical crown that graduallylowers from the middle of the top to the periphery. The first air vent41 is disposed at a position corresponding to the area of rotation ofthe propeller 30, as long as the side projection of the first air vent41 and the side projection of the propeller 30 at least partiallyoverlap. Therefore, the first air vent 41 can guide the airflowgenerated when the propeller 30 of the UAV 100 rotates into the housing40 through the first air vent 41.

In some embodiments, the second plate 44 may extend in a horizontaldirection away from the connection wall 45 or obliquely downward awayfrom the connection wall 45, so as not to block the airflow runningalong the tangential direction of the area of rotation of the propeller30 entering the housing 40 through the first air vent 41. It caneffectively change the flow direction of the downwash flow generatedwhen the propeller rotates and make the part of the downwash flow afterchanging the flow direction enter the housing 40 through the first airvent 41.

In some embodiments, the connection wall 45 may be perpendicular to thefirst plate 43 and the second plate 44. In some other embodiments, theconnection wall 45 may also be set obliquely relative to the first plate43 and the second plate 44, which can be set according to the design ofthe housing 40 and not limited here.

Further, based on other height designs of the propeller 30 and the topof the UAV 100, the first air vent 41 may also be provided at the sidewall of the UAV, which is not limited herein.

In the example shown in FIG. 3 , the first plate 43, the second plate44, and the connection wall 45 may be an integral piece formedintegrally. In another embodiment, the first plate body 43, the secondplate body 44, and the connection wall 45 may also be assembled parts.

In some embodiments, the first air vent 41 may be provided at an end ofthe housing 40 opposite to an end of the housing 40 connected to thecarrier 90 that supports the load, and the second air vent 42 may beprovided at a corresponding area of the housing 40 connected to thecarrier 90, which is not limited thereto. For example, in some otherembodiments, the first air vent 41 is provided at the end of the housing40 connected to the carrier 90 that supports the load, and the secondair vent 42 is provided at the end of the housing 40 opposite to the endof the housing 40 connected to the carrier 90. In some embodiments, thelocations of the first air vent 41 and the second air vent 42 can bedesigned according to the specific needs. In some embodiments, as shownin FIG. 2 , the carrier 90 is a gimbal, and the load is a camera. Asshown in FIG. 3 , the second air vent 42 is provided at a correspondingarea of the housing 40 connected to the gimbal. An opening at one sideof the second air vent 42 faces the corresponding area, and an openingat the other side of the second air vent 42 faces the chamber of thehousing 40. Since the gimbal can be arranged at the bottom of the UAV,when observed from the bottom of the UAV 100, the corresponding area isthe bottom area where the UAV 100 is connected to the gimbal.

In some embodiments, the carrier 90 may be provided at the bottom of thefront end of the housing 40, and the first air vent 41 may be providedat the rear end of the housing 40. Since there is a slot foraccommodating the gimbal at the connection area between the gimbal andthe bottom of the housing 40, this part can be utilized to arrange thesecond air vent 42. That is, the second air vent 42 is provided at theslot of the bottom of the housing 40 and opens towards the inner chamberof the housing 40, so as to maintain the appearance of the originaldesign of the UAV as much as possible, which is beneficial to simplifythe manufacturing process of the housing 40, and can effectively use theoriginal design process.

In some embodiments, in addition to the positions described above, thesecond air vent 42 can also be provided at other positions of thehousing 40 in practical applications, as long as it can cooperate withthe first air vent 41 to form a corresponding air duct for heatdissipation, which is not limited here.

In the example shown in FIG. 3 , the housing 40 includes a shield 75,and the shield 75 is a part of the top of the housing 40, such as beingconnected to the cover 48 of the housing 40 (may be located below thecover 48). When the cover 48 is connected to the casing 47, the shield75 can be directly disposed above the carrier 90, and a second air vent42 can be provided at the shield 75. The opening direction of the secondair vent 42 may be parallel to the vertical direction, so as to achieveefficient heat dissipation by simply modifying the structure of theproduct. In some other embodiments, the opening direction of the secondair vent 42 may also be arranged along the horizontal direction orobliquely, which is not limited here.

In addition to the positions described above, in practical applications,the shield 75 may also be provided at the bottom of the housing 40. Theshield 75 may serve as a part of the connection between the bottom ofthe housing 40 and the inner chamber of the housing 40, and maycooperate with the bottom of the housing 40 to form a slot foraccommodating the carrier 90, which is not limited herein.

Further, the housing 40 may also be provided with a third air vent 46,which is used to cooperate with the first air vent 41. The third airvent 46 is provided near the end of the housing 40, that is, the end ofthe body of the UAV 100, so that part of the airflow formed when thepropeller 30 rotates can also enter the housing 40 through the third airvent 46. The first air vent 41 and the third air vent 46 may be locatedat the same end of the body, and the third air vent 46 may not becoplanar with the first air vent 41. As shown in FIG. 3 , both the firstair vent 41 and the third air vent 46 may be located at the rear end ofthe body, but the first air vents 41 are located at both sides of thethird air vent 46, and the second air vent 42 can be located at thefront end of the body, so as to use at least part of the body to form acorresponding cooling air duct to improve the heat dissipationefficiency.

In practical applications, the first air vent 41 and the third air vent46 may also cooperate to form one air vent, and the air vent may conformto the shape of the first air vent 41 and the third air vent 46, such asa U-shaped air vent. Other shapes are also possible, which are notlimited here.

In some embodiments, as shown in FIG. 3 , the heat dissipation structurefurther includes a heat sink 65 disposed at the housing 40, and the heatsink 65 is used to dissipate heat from the heating element 50. The heatsink 65 is provided with a plurality of heat dissipation fins 66, and aplurality of heat dissipation channels 67 are formed between theplurality of heat dissipation fins 66 to increase the heat dissipationarea. The heat sink 65 can be fixed to the heating element 50 by thermalconductive adhesive or another manner, or it can be provided with acorresponding mounting portion, such as a bolt hole, so that the heatsink 65 can be fixed to the housing 40 or the heating element (such asflight control circuit board) through a bolt, thereby improving theconnection strength of the heat sink 65.

During operation, after the UAV is started, the propeller 30 rotates,and the airflow generated when the propeller 30 rotates enters theinterior of the housing 40 from the first air vent 41, and the airflowblows through the multiple heat dissipation channels formed by the heatsink 65 to exchange heat with the heat sink 65 and then flows out of thehousing 40 from the second air vent 42, so as to bring the heatgenerated by the heating element 50 out of the housing 40.

In the example shown in FIG. 3 , in order to reduce or eliminate theelectromagnetic interference of the electromagnetic signal generated bythe heating element 50 on the external circuit or the electromagneticinterference of the external electromagnetic signal on the heatingelement 50, the housing 40 is also provided with a shield cover 85. Theshield cover 85 may be provided between the heat sink 65 and the heatingelement 50. A thermal conductive adhesive is provided between the shieldcover 85 and the heat sink 65, and a heat dissipation boss (not shown inthe figure) that cooperates with the heating element 50 is also providedon the shield cover 85. In this way, the heat of the heating element 50can be quickly and efficiently conducted to the heat sink 65 via theshield cover 85.

Further, in some embodiments, as shown in FIG. 3 , the heat dissipationstructure further includes a cooling fan 70 provided at the housing 40.Based on the different models of the UAV and the internal structuredesign, the cooling fan can have different designs.

In some embodiments, the cooling fan 70 may be close to the first airvent 41 for discharging the inlet airflow from the first air vent 41(this inlet airflow may include the airflow generated when the propeller30 rotates) out of the second air vent 42. During the flight of the UAV100, the airflow generated by the rotation of the propeller 30 will gothrough the first air vent 41 and be discharged out of the housing 40through the second air vent 42. At this time, if the cooling fan isstarted, and the cooling direction of the cooling fan 70 is the same asthe cooling direction of the airflow generated when the propeller 30rotates, the heat dissipation efficiency is improved.

In some embodiments, as shown in FIG. 3 , the cooling fan 70 is arrangedclose to the second air vent 42 for discharging the airflow from thesecond air vent 42 out of the first air vent 41. After the cooling fan70 is started, the cold air is sucked in through the second air vent 42and pressurized by the cooling fan 70 to form a high-pressure coolingairflow, then flows through the heat sink 65 to dissipate heat from theheating element 50, and then flows out of the housing 40 through thefirst air vent. In this manner, the cooling direction of the cooling fan70 is opposite to the cooling direction of the airflow generated by therotation of the propeller 30, but it can be understood that when the UAVflies, the airflow pressure generated by the rotation of the propeller30 may be greater than the airflow pressure formed by the cooling fan70. In order to save energy, the cooling fan 70 may not be started whenthe UAV flies and may be started for heat dissipation when the UAV isnot flying but needs to be cooled.

In some embodiments, the cooling fan 70 may be glued on the shield cover85 or the heating element 50, or another fixing manner may be used,which is not limited thereto. As described above, in some embodiments,the cooling fan 70 is arranged close to the second air vent 42. In theseembodiments, if the second air vent 42 is disposed at the shield 75, thecooling fan 70 is located at a side of the shield 75. The shield 75 maybe a dust shield and a plurality of grilles are provided at the secondair vent 42 so as to let the cooling airflow in and out while blockingdust. The cooling fan 70 is a centrifugal fan. In some otherembodiments, the cooling fan 70 may include an axial fan or another typeof fan.

In some embodiments, as shown in FIG. 3 , a wind shield boss 68 isprovided between the cooling fan 70 and the heat sink 65, and thematerial of the wind shield boss 68 may include, but is not limited to,foam. The wind shield boss 68 is provided with an opening correspondingto the air vent on the side wall of the cooling fan 70, and the openingconnects with a plurality of heat dissipation channels 67 formed by theheat sink 65. In some embodiments, the wind shield boss 68 can isolatethe outside cold air flowing into the housing 40 and the outside coldair after heat transfer, thereby improving the heat dissipationefficiency of the cooling fan 70.

In order to cooperate with the design of the first air vent 41, or thedesign of the first air vent 41 and the third air vent 46, the heatdissipation structure further includes a shunt structure 60 provided atthe housing 40, and the shunt structure 60 may be used to divide andguide the cooling airflow (the cooling airflow may be the airflowgenerated when the propeller 30 rotates (also referred to as“propeller-generated airflow”) or the airflow generated when the coolingfan 70 rotates (also referred to as “fan-generated airflow”) passing bythe shunt structure 60, so as to discharge the cooling airflow out ofthe housing 40 efficiently in multiple directions. Referring to FIG. 3 ,the shunt structure 60 is close to the first air vent 41, and theshunting direction of the shunt structure 60 can correspond to theposition direction of the first air vent 41 and the position directionof the third air vent 46, so that the cooling airflow can be dischargedthrough the first air vent 41 and the third air vent 46 moreeffectively.

The shunt structure 60 includes an electronic device, but it is notlimited thereto. For example, the shunt structure 60 may also be aninternal structure provided in the housing 40 to guide the coolingairflow. In some embodiments, the shunt structure 60 may include apositioning device, such as a GPS device, a Beidou positioning device,and so on. The shunt structure 60 can also be another electronic device.

In the example shown in FIG. 3 , the shunt structure 60 may be a GPSdevice, and the GPS device may be fixed to the shield cover 85 byfasteners. The shunt structure 60 can also be connected and fixed to theshield cover 85 or the heating element 50 or other elements by, forexample, bonding. A first part 61 may be a circuit board, and a secondpart 62 may be a chip.

In some embodiments, in order to realize the shunt design of the shuntstructure 60, in an embodiment, the shunt structure 60 includes thefirst part 61 and the second part 62 disposed at the first part 61. Thefirst part 61 and the second part 62 cooperate to form a plurality ofshunting directions. The plurality of shunting directions cooperate withthe first air vent 41, or with the first air vent 41 and the third airvent 46, so that heat can be dissipated more efficiently.

In some embodiments, as shown in FIG. 3 , the second part 62 may be asquare structure, and the opposite angles of the square structure may beclose to the side of the first part 61 respectively (e.g., instead ofthe parallel overlapping design of the second part 62 and the first part61, the second part 62 is turned forty five degrees clockwise orcounterclockwise relative to the first part 61). That is, a pair ofadjacent sides of the second part 62 cooperate with the first part 61,so that airflows with directions of 45 degrees are formed along theadjacent sides of the second part 62 at one side of the first part 61,and another airflow direction is formed on the top of the second part62. Therefore, the cooling airflow passing through the shunt structure60 can be diverted and guided into three airflows. That is, the airflowdirections of two adjacent sides of the square structure respectivelycorrespond to the position directions of the corresponding first airvents 41, and the airflow direction at the top of the square structurecorresponds to the position and direction of the third air vents 46. Thesecond part 62 may also have another shape, such as a diamond shape, atriangular shape, etc., as long as the second part 62 has a structurethat divides and guides the cooling airflow. The specific shape is notlimited.

In some embodiments, as shown in FIG. 3 , the heat dissipation structurefurther includes a wind shield 69, and the wind shield 69 is used toform a closed air duct from the heat dissipation channel 67 to the firstair vent 41. The wind shield 69 includes a first part 691 and a secondpart 692. The first part 691 covers the heat sink 65 and closes the topof the heat dissipation channel 67. The second part 692 may have aU-shaped structure and surround the GPS device at the side away from theheat sink 65 and two adjacent sides, so that the cooling airflow isrestricted to the closed air duct, and is discharged out of the housing40 from the first air vent 41, or the first air vent 41 and the thirdair vent 46, to avoid the diffusion of the cooling airflow to the otherlocations of the housing 40, thereby improving the cooling efficiency ofthe heating element 50.

FIG. 4 is an enlarged view of a part of the housing of the UAV describedabove in connection with FIG. 3 . Referring to FIG. 4 , the first airvent 41 is provided with a deflector 411 extending from the direction ofthe airflow generated when the propeller 30 rotates to the inside of thehousing 40. The arrangement of the deflector 411 is conducive to guidingthe airflow into the housing 40.

Further, the extension direction of the first air vent 41 is consistentwith the direction of the airflow generated when the propeller 30rotates, so that the airflow receives less resistance when entering thehousing 40 through the first air vent 41, and more airflow can enter thehousing 40, as a result, the cooling efficiency is high.

The UAV 100 needs heat dissipation in a flight state, and also needsheat dissipation in a standby state. The standby state refers to a statewhen the UAV 100 has been powered on and has not yet taken off. Based onthe above structure, the heat dissipation manners of the UAV 100 in twostates will be described separately.

When the UAV 100 is in a standby state, the cooling fan 70 may be usedfor heat dissipation. The cooling fan 70 is started and after thecooling fan 70 starts to rotate, the cooling airflow is sucked inthrough the second air vent 42. After the cooling airflow is pressurizedby the cooling fan 70, it flows through the heat dissipation channels 67through the opening of the wind shield boss 68, and exchange heat withthe heating element 50 through the heat dissipation fins 66, and then isdischarged from the first air vent 41 and the third air vent 46 underthe dividing and guiding of the shunt structure 60. The cooling airflowcan be divided into three airflows when passing through the shuntstructure 60. One airflow flows through the top surface of the secondpart 62 and is discharged from the third air vent 46, and the other twoairflows flow through the two adjacent sides of the second part 62 andare discharged from the first air vents 41 on both sides of the thirdair vent 46, thereby bringing the heat generated by the heating element50 out of the body, lowering the temperature in the housing 40, andensuring that the heating element 50 can work normally and stably. Asshown in FIG. 3 , the heat dissipation direction may be from the bottomof the front end of the UAV 100 to the front end of the second air vent42 and to the rear end of the first air vent 41.

When the UAV 100 is in a flight state, the cooling fan 70 may be turnedon or off. In some embodiments, in order to increase the endurance ofthe UAV, the cooling fan can be turned off. At this time, the propeller30 rotates to generate an area of rotation, and an airflow running alongthe tangential direction of the area of rotation, or an airflow runningalong the tangential direction of the area of rotation and a downwashflow can enter the housing 40 through the first air vent 41. The airflowpasses through the heat dissipation channels 67 of the heat sink 65under the guidance of the shunt structure 60, and exchanges heat withthe heating element 50 through the heat dissipation fins 66, and then isdischarged from the second air vent 42, thereby bringing the heatgenerated by the heating element 50 out of the body, lowering thetemperature in the housing 40, and ensuring that the heating element 50can work normally and stably. As shown in FIG. 3 , the heat dissipationdirection may be from the first air vent 41 at the rear end of the UAV100 to the second air vent 42 at the front end to the bottom of thefront end. In practical applications, different heat dissipation mannerscan be selected according to the working state of the UAV 100, theoperation state of the cooling fan, and other information.

Based on the above-described different heat dissipation manners, a heatdissipation method is provided according to the present disclosure. FIG.5 is a flowchart of the heat dissipation method provided by the presentdisclosure. The method can be implemented by, e.g., a UAV flight controlsystem.

Referring to FIG. 5 , at 501, state information of the UAV is detected.

In some embodiments, a cooling fan may be provided at the housing of theUAV for dissipating heat from a heating element, and a cooling air ductmay be provided for dissipating heat from the heating element utilizingthe airflow generated when the propeller of the UAV rotates. For theUAV, the following heat dissipation manners can be provided: using thecooling fan to dissipate heat from the heating element, using theairflow generated when the propeller rotates to dissipate heat from theheating element, and using both. For a certain state of the UAV, one ofthe above heat dissipation manners for cooling may be chosen. Thus, thestate information of the UAV can be detected to adjust the heatdissipation manner according to the state information.

At 502, an operation state of the cooling fan is controlled according tothe state information.

In some embodiments, after the state information of the UAV is detected,the operation state of the cooling fan can be controlled according tothe state information.

In some embodiments, controlling the operation state of the cooling fanmay include starting the cooling fan, turning off the cooling fan, andadjusting the rotation speed of the cooling fan. Therefore, according tothe state information, through the above-described control of thecooling fan, such as starting the cooling fan or adjusting the rotationspeed of the cooling fan, the cooling fan can realize the cooling of theheating element of the UAV, or the cooling fan and the airflow generatedduring rotation of the propeller can realize the cooling of the heatingelements of the UAV. When the cooling fan is turned off, the airflowgenerated during rotation of the propeller can realize the cooling ofthe UAV.

Therefore, when the airflow generated by the rotation of the propelleris used to dissipate heat from the heating elements in the UAV, thepower consumption of the UAV can be saved, which is helpful inincreasing the flight time of the UAV. When the propeller is notworking, but the UAV needs heat dissipation, the cooling fan can be usedto dissipate heat to meet the heat dissipation need. When the above twoheat dissipation manners are both used and the heat dissipationdirection of the cooling fan and the heat dissipation direction of theairflow generated when the propeller rotates are the same, the heatdissipation efficiency of the UAV can be further improved.

Based on the description of the above heat dissipation manners,different controls according to the state information of the UAV aredescribed as follows.

in some embodiments, the state information of the UAV includes a workingstate of the UAV. In some embodiments, the working state of the UAV mayinclude a flight state or a standby state. The flight state refers to astate in which the UAV's power components provide the flying power ofthe UAV during the flight and the standby state refers to a state inwhich the UAV has been powered on but has not yet flown.

In some embodiments, when the working state of the UAV is the flightstate, then controlling the operation state of the cooling fan accordingto the state information (502) includes turning off the cooling fan inresponse to the working state being the flight state. At this time, theairflow generated when the propeller of the UAV rotates can be used todissipate heat from the heating element. Because the cooling fan isturned off, the power consumption caused by turning on the cooling fancan be reduced, which is conducive to improving the endurance of theUAV.

In some embodiments, when the working state of the UAV is the standbystate, then controlling the operation state of the cooling fan accordingto the state information (502) includes, turning on the cooling fan inresponse to the working state being the standby state. At this time, thepropeller of the UAV is not rotating but the heating element of the UAVmay still generate a large amount of heat, and hence the cooling fan canbe used to dissipate the heat generated by the heating element.

In some embodiments, only the working state of the UAV may need to bedetected, and the cooling fan may be turned on or off according to theworking state of the UAV 100.

In some embodiments, the state information of the UAV includes theworking state of the UAV and the temperature information of the heatingelement.

In some embodiments, controlling the operation state of the cooling fanaccording to the state information (502) includes turning off thecooling fan in response to the temperature information indicating thatthe temperature of the heating element is lower than a first threshold,or starting the cooling fan in response to the temperature informationindicating the temperature of the heating element is not lower than thefirst threshold. The first threshold can be determined according to theworking state of the UAV. That is, the value of the first threshold candepend on whether the UAV is in the flight state or the standby state.For example, when the UAV is in the flight state, if the temperatureinformation indicates that the temperature of the heating element isless than 65 degrees, the cooling fan can be turned off, and the airflowgenerated when the propeller rotates is used to dissipate heat. When thetemperature information indicates that the temperature of the heatingelement is not less than 65 degrees, the cooling fan can be started, andthe airflow generated by the propeller rotation and the cooling fan canbe used jointly to dissipate heat to improve heat dissipationefficiency. When the UAV is in the standby state, if the temperatureinformation indicates that the temperature of the heating element islower than 60 degrees, the cooling fan can be turned off, and when thetemperature information indicates that the temperature of the heatingelement is not lower than 60 degrees, the cooling fan can be started andused for heat dissipation. The first threshold described above is onlyan example. In practical applications, the first threshold may be setaccording to the working state of the UAV and is not limited here.

The temperature information of the heating element may be temperatureinformation about the surface of the heating element (such astemperature information obtained from one or more points on thesurface), or temperature information of the environment in which theheating element is located, or other temperature information as long asthe temperature information can indicate the relevant temperature of theheating element to determine whether the heating element can withstandthe relevant temperature, which is not limited here.

Further, when the temperature information indicates that the temperatureof the heating element is not lower than the first threshold, startingthe cooling fan may include determining a target speed of the coolingfan according to the correspondence between the temperature informationand the speed of the cooling fan, and controlling the cooling fan to runaccording to the target speed. The correspondence can be determined bythe working state.

In some embodiments, when the working state of the UAV is the flightstate, if the cooling fan is started, the cooling fan can be controlledto run at a certain preset speed according to the temperatureinformation, so as to simultaneously use the cooling fan and the airflowgenerated when the propeller of the UAV rotates to dissipate heat fromthe heating element. When the working state of the UAV is the standbystate, the cooling fan can be started and controlled to run at adifferent preset speed according to the temperature information. At thistime, the propeller has not yet rotated, but the different coolingefficiency of the cooling fan can be used to dissipate heat from theheating element.

In the corresponding working state of the UAV, the temperature level canbe set according to the corresponding first threshold, and thecorresponding rotation speed of the cooling fan can be set at thecorresponding temperature level. For example, when the working state ofthe UAV is the standby state, and when the temperature informationindicates that the temperature of the heating element is between 60degrees and 80 degrees, the cooling fan can be controlled to run at 60%of its maximum speed, and the cooling fan can dissipate heat from theheating element at a heat dissipation efficiency corresponding to 60% ofits maximum rotation speed. When the temperature information indicatesthat the temperature of the heating element is higher than 80 degrees,the cooling fan can be controlled to run at its maximum speed, and thecooling fan can dissipate heat from the heating element at a heatdissipation efficiency corresponding to the maximum speed. In some otherembodiments, the correspondence between the temperature information inthe standby state and the rotation speed of the cooling fan may be setaccording to specific needs and is not limited thereto.

For another example, when the working state of the UAV is the flightstate and when the temperature information indicates that thetemperature of the heating element is between 65 degrees and 85 degrees,the cooling fan is controlled to run at 60% of its maximum speed, andairflow generated by the operation of the cooling fan and the airflowgenerated by the rotation of the propeller are used to dissipate heatfrom the heating element. When the temperature information indicatesthat the temperature of the heating element is higher than 85 degrees,the cooling fan is controlled to run at its maximum speed, and theairflow generated by the operation of the cooling fan and the airflowgenerated by the rotation of the propeller are used to dissipate heatfrom the heating element. In some other embodiments, in the flightstate, the correspondence between the temperature information and therotation speed of the cooling fan may be set according to specific needsand is not limited thereto.

In some embodiments, the airflow generated by the cooling fan and theairflow generated by the rotation of the propeller can share a coolingair duct. Then, when the air inlet of the cooling fan is close to theinlet of the airflow, the cooling direction of the cooling fan can bethe same as the cooling direction of the airflow. Thus, the cooling fancan be selectively turned on or off in order to use the airflowgenerated by the rotation of the propeller to dissipate heat, or use thecooling fan to dissipate heat, or use the airflow generated by thecooling fan and also by the rotation of the propeller to dissipate heat.When the air inlet of the cooling fan is close to the outlet of theairflow, the cooling direction of the cooling fan is opposite to thecooling direction of the airflow. At this time, the cooling fan can beselectively turned on or off in order to use the airflow generated whenthe propeller rotates to dissipate heat or use the cooling fan todissipate heat.

When the airflow generated by the cooling fan and the airflow generatedwhen the propeller rotates share the cooling air duct, the cooling fancan be arranged at different positions to meet the design of the coolingdirection. In practical applications, the cooling air duct correspondingto the cooling fan may be different from the cooling air ductcorresponding to the airflow generated when the propeller rotates, whichis not limited here.

The above heat dissipation method can be applied to any heat dissipationstructure or UAV with a cooling fan and a cooling air duct thatdissipates heat from the heating element using the airflow generatedwhen the propeller of the UAV rotates. It can also be applied to theheat dissipation structure and the UAV in the present disclosure.

In some embodiments, the housing to which the heat dissipation method isapplied includes the first air vent 41 and the second air vent 42 asshown in FIG. 3 . The first air vent 41 is used to guide the airflowgenerated when the propeller 30 of the UAV 100 rotates into the housing40 through the first air vent 41. The second air vent 42 is used todischarge the airflow after heat transfer with the heating element 50out of the housing 40. The side projection of the first air vent 41 andthe side projection of the propeller 30 at least partially overlap.

In some embodiments, as shown in FIG. 3 , the height of the upper end ofthe first air vent 41 is higher than or equal to the height of the upperend of the propeller 30, and the height of the lower end of the firstair vent 41 is not higher than the height of the lower end of thepropeller 30.

In some embodiments, as shown in FIG. 3 , the top of the housing 40 isprovided with the first plate 43, the second plate 44 and the connectionwall 45 connecting the first plate 43 and the second plate 44. The firstair vent 41 is disposed at the connection wall 45, and the platformheight of the first plate 43 is different from the platform height ofthe second plate 44.

In some embodiments, as shown in FIG. 3 , the platform height of thefirst plate 43 is higher than the height of the upper end of thepropeller 30, and when the propeller 30 rotates to form an area ofrotation, the projection of the second plate 44 on the area of rotationat least partially overlaps with the area of rotation.

In some embodiments, as shown in FIG. 3 , the first air vent 41 isprovided with a deflector extending from the direction of the airflowgenerated when the propeller 30 rotates to the inside of the housing 40.

In some embodiments, as shown in FIG. 3 , the housing 40 is furtherprovided with a third air vent 46, which is used to cooperate with thefirst air vent 41.

In some embodiments, as shown in FIG. 3 , a shunt structure 60 isprovided at the housing 40, and the shunt structure 60 is used to divideand guide the cooling airflow passing through the shunt structure 60.

FIG. 6 shows a heat dissipation device consistent with the presentdisclosure. The heat dissipation device is applied to a UAV. The heatdissipation device includes a processor 610 (such as a single-core ormulti-core processor). The processor 610 can communicate with a coolingfan 620 built in the UAV.

The heat dissipation device may include the cooling fan 620 or may be aseparate component of the UAV from the cooling fan 620, which is notlimited here.

The processor 610 may be a central processing unit (CPU). The processor610 may further include a chip. The above-described chip may be anapplication-specific integrated circuit (ASIC), a programmable logicdevice (PLD), or a combination thereof. The PLD may be a complexprogrammable logic device (CPLD), a field-programmable gate array(FPGA), a generic array logic (GAL), or any combination thereof.

Further, the processor 610 includes one or more, working individually orcollectively.

In some embodiments, the processor 610 is used to detect the stateinformation of the UAV and control the operation state of the coolingfan 620 according to the state information. The housing of the UAV isprovided with a cooling fan 620 that dissipates heat from the heatingelement and a cooling air duct that dissipates heat from the heatingelement by using the airflow generated when the propeller of the UAVrotates.

In some embodiments, the state information includes a working state ofthe UAV.

In some embodiments, when the state information includes the workingstate, the processor 610 is configured to turn off the cooling fan 620if the working state is a flight state or start the cooling fan 620 ifthe working state is a standby state.

In some embodiments, the state information includes the working state ofthe UAV or temperature information of the heating element.

In some embodiments, when the state information includes the workingstate of the UAV and the temperature information of the heating element,the processor 610 is configured to turn off the cooling fan 620 if thetemperature information indicates that the temperature of the heatingelement is lower than a first threshold, or start the cooling fan 620 ifthe temperature information indicates that the temperature of theheating element is not lower than the first threshold. The firstthreshold is determined according to the working state.

In some embodiments, the processor 610 is configured to determine atarget speed of the cooling fan 620 according to the correspondencebetween the temperature information and the rotation speed of thecooling fan 620 and control the cooling fan 620 to run according to thetarget speed. The correspondence can be determined by the working state.

In some embodiments, the working state includes a flight state or astandby state.

In some embodiments, the cooling fan 620 shares a cooling air duct withthe airflow.

In some embodiments, when the air inlet of the cooling fan 620 is closeto the inlet of the airflow, the cooling direction of the cooling fan620 is the same as the cooling direction of the airflow.

In some embodiments, when the air inlet of the cooling fan 620 is closeto the outlet of the airflow, the cooling direction of the cooling fan620 is opposite to the cooling direction of the airflow.

In some embodiments, the housing is provided with a first air vent and asecond air vent. The first air vent is used to guide the airflowgenerated when the propeller of the UAV rotates into the housing throughthe first air vent. The second air vent is used to discharge the airflowafter heat transfer with the heating element out of the housing. Theside projection of the first air vent and the side projection of thepropeller at least partially overlap.

In some embodiments, the height of the upper end of the first air ventis higher than or equal to the height of the upper end of the propeller,and the height of the lower end of the first air vent is not higher thanthe height of the lower end of the propeller.

In some embodiments, the top of the housing is provided with a firstplate, a second plate and a connection wall connecting the first plateand the second plate. The first air vent is disposed at the connectionwall, and the platform height of the first plate is different from theplatform height of the second plate.

In some embodiments, the platform height of the first plate is higherthan the height of the upper end of the propeller, and when thepropeller rotates to form an area of rotation, the projection of thesecond plate on the area of rotation overlaps with the area of rotation.

In some embodiments, the first air vent is provided with a deflectorextending from the direction of the airflow generated when the propellerrotates to the inside of the housing.

In some embodiments, the housing is further provided with a third airvent, which is used to cooperate with the first air vent.

In some embodiments, a shunt structure is provided at the housing, andthe shunt structure is used to divide and guide the cooling airflowpassing through the shunt structure.

Based on the description of the above heat dissipation device, anunmanned aerial vehicle (UAV) is further provided according to anembodiment of the present disclosure. The UAV includes a body, an armconnected to the body, and a propeller connected to the arm, and mayalso include the above heat dissipation device.

If a module/unit integrated with the heat dissipation device isimplemented in a form of a software functional unit and sold or used asa standalone product, it may be stored in a computer-readable storagemedium. All or part of the processes in the methods of the aboveembodiments of the present disclosure can also be implemented by acomputer program instructing relevant hardware. The computer program canbe stored in a computer-readable storage medium. When the program isexecuted by the processor, the processes of the foregoing method of theembodiments may be implemented. The computer program includes computerprogram code, and the computer program code may be in the form of sourcecode, object code, executable file, or some intermediate form. Thecomputer-readable medium may include any entity or device capable ofcarrying the computer program code, such as a recording medium, a Udisk, a portable hard disk, a magnetic disk, an optical disk, a computermemory, a read-only memory (ROM), a random-access memory (RAM),electrical carrier signals, telecommunications signals and softwaredistribution media, etc. The content contained in the computer-readablemedium can be appropriately increased or decreased according to therequirements of legislation and patent practice in jurisdictions. Forexample, in some jurisdictions, according to legislation and patentpractice, computer-readable media does not include electrical carriersignals and telecommunications signals.

In the present disclosure, relational terms such as “first” and “second”are only used to distinguish one entity or operation from another entityor operation, and do not necessarily require or imply that there is anysuch actual relationship or order between these entities or operations.The term “comprising,” “including” or any other variation thereof isnon-exclusive inclusion, such that a process, method, article, or devicethat include a series of elements include not only those elements butalso other elements that are not explicitly listed, or elements that areinherent to such a process, method, article, or device. Without morerestrictions, the elements defined by the sentence “including a . . . ”do not exclude the existence of other identical elements in the process,method, article, or equipment that includes the elements.

The methods and devices provided by the present disclosure are describedin detail above. Specific examples are used to explain the principlesand implementation of the present disclosure. The descriptions of theabove embodiments are only for facilitating the understanding of thepresent disclosure; meanwhile, for a person of ordinary skill in theart, according to the present disclosure, there will be changes in thespecific implementation and application. In summary, the content of thisspecification is not a limitation to this disclosure.

What is claimed is:
 1. A heat dissipation structure comprising: ahousing configured to accommodate a heating element of an unmannedaerial vehicle (UAV), the housing including: a first air vent configuredto guide an airflow into the housing, the airflow including apropeller-generated airflow generated by a propeller of the UAV duringrotation, a side projection of the first air vent on a side of thehousing at least partially overlapping a side projection of thepropeller on the side of the housing, the housing and the propellerbeing located at two opposite ends of an arm of the UAV in alongitudinal direction of the arm; and a second air vent configured toguide the airflow out of the housing.
 2. The heat dissipation structureof claim 1, wherein a height of an upper end of the first air vent ishigher than or equal to a height of an upper end of the propeller, and aheight of a lower end of the first air vent is not higher than a heightof a lower end of the propeller.
 3. The heat dissipation structure ofclaim 2, wherein: the housing further includes a first plate, a secondplate, and a connection wall connecting the first plate and the secondplate at a top of the housing; the first air vent is disposed at theconnection wall; and a platform height of the first plate is differentfrom a platform height of the second plate.
 4. The heat dissipationstructure of claim 3, wherein: the platform height of the first plate ishigher than the height of the upper end of the propeller; and aprojection of the second plate on a plane on which an area of rotationof the propeller lies at least partially overlaps with the area ofrotation.
 5. The heat dissipation structure of claim 3, wherein thesecond plate extends in a horizontal direction away from the connectionwall or obliquely downward away from the connection wall.
 6. The heatdissipation structure of claim 3, wherein the first plate, the secondplate, and the connection wall are an integral piece.
 7. The heatdissipation structure of claim 1, wherein: the first air vent includes adeflector extending into the housing along a direction of thepropeller-generated airflow; and an extension direction of the first airvent is consistent with the direction of the propeller-generatedairflow.
 8. The heat dissipation structure of claim 1, wherein thehousing further includes a third air vent configured to cooperate withthe first air vent, the third air vent is provided at an end of thehousing, and the third air vent is not coplanar with the first air vent.9. The heat dissipation structure of claim 1, further comprising: ashunt structure in the housing and configured to divide and guide theairflow passing through the shunt structure.
 10. The heat dissipationstructure of claim 9, wherein the shunt structure is below the first airvent, and a shunting direction of the shunt structure corresponds to aposition direction of the first air vent.
 11. The heat dissipationstructure of claim 10, wherein the shunt structure includes a first partand a second part disposed at the first part, and the first part and thesecond part cooperate to form a plurality of shunting directions. 12.The heat dissipation structure of claim 11, wherein the second part is asquare structure, and each of vertex angles of the square structure isarranged at a side of the first part.
 13. The heat dissipation structureof claim 9, wherein the shunt structure includes a positioning device.14. The heat dissipation structure of claim 1, wherein: the first airvent is provided at an end of the housing that is opposite to an end ofhousing connected to a carrier that supports a load; the second air ventis provided at a corresponding area of the housing connected to thecarrier; and an opening direction of the second air vent is parallel toa vertical direction.
 15. The heat dissipation structure of claim 1,further comprising: a heat sink disposed at the housing and configuredto dissipate heat from the heating element.
 16. The heat dissipationstructure of claim 15, further comprising: a wind shield; wherein: theheat sink includes a plurality of heat dissipation fins and a pluralityof heat dissipation channels formed among the plurality of heatdissipation fins; and the wind shield forms a closed air duct from theheat dissipation channels to the first air vent.
 17. The heatdissipation structure of claim 1, further comprising: a cooling fanprovided at the housing and located: below the first air vent andconfigured to drive an inlet airflow from the first air vent to thesecond air vent; or below the second air vent and configured to drivethe inlet airflow from the second air vent to the first air vent.
 18. Anunmanned aerial vehicle (UAV) comprising: an arm; a housing connected toa first end of the arm; a heating element accommodated in the housing;and a propeller connected to a second end of the arm, the first end andthe second end being opposite to each other in a longitudinal directionof the arm; wherein the housing includes: a first air vent configured toguide an airflow into the housing, the airflow including apropeller-generated airflow generated by the propeller during rotation,a side projection of the first air vent on a side of the housing atleast partially overlapping a side projection of the propeller on theside of the housing; and a second air vent configured to guide theairflow out of the housing.
 19. The heat dissipation structure of claim1, wherein: a projection of the first air vent on a plane perpendicularto a plane on which an area of rotation of the propeller lies at leastpartially overlaps the projection of the propeller on the planeperpendicular to the plane on which the area of rotation of thepropeller lies.
 20. A heat dissipation structure comprising: a housingconfigured to accommodate a heating element of an unmanned aerialvehicle (UAV), the housing including: a first air vent configured toguide an airflow into the housing, the airflow including apropeller-generated airflow generated by a propeller of the UAV duringrotation, a side projection of the first air vent on a side of thehousing at least partially overlapping a side projection of thepropeller on the side of the housing, the housing and the propellerbeing located at two opposite ends of an arm of the UAV in alongitudinal direction of the arm; and a second air vent configured toguide the airflow out of the housing; wherein a projection of thehousing on a plane on which an area of rotation of the propeller lies atleast partially overlaps the area of rotation of the propeller.